Launch lock assemblies with reduced preload and spacecraft isolation systems including the same

a technology of preload reduction and assembly, which is applied in the field of spacecraft isolation systems, can solve the problems of limited length of axial gap provided by axial gap amplification devices, and achieve the effect of increasing the length of axial gap

Active Publication Date: 2016-10-25
HONEYWELL INT INC
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Therefore, the increase in length of the axial gap provided by the axial gap amplification device is limited by the preload that can be applied thereto.

Method used

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  • Launch lock assemblies with reduced preload and spacecraft isolation systems including the same
  • Launch lock assemblies with reduced preload and spacecraft isolation systems including the same
  • Launch lock assemblies with reduced preload and spacecraft isolation systems including the same

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[0025]The following Detailed Description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the preceding Background or the following Detailed Description.

[0026]FIGS. 1 and 2 are simplified schematics of a spacecraft isolation system 20 in locked (pre-launch) and unlocked (design, isolated) positions, respectively, as illustrated in accordance with an exemplary embodiment of the present invention. When in the unlocked position shown in FIG. 2, spacecraft isolation system 20 reduces the transmission of vibrations between a payload 22 and a host spacecraft 24. In the illustrated example, isolation system 20 includes a plurality of single degree of freedom or axially-damping vibration isolators 26, which are mechanically coupled to and collectively support payload 22. More specifically, vibration isolations 26 may be pivotally coupled to a payloa...

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Abstract

Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.

Description

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT[0001]This invention was made with Government support under NNG09HR00C awarded by NASA. The Government has certain rights in this invention.TECHNICAL FIELD[0002]The present invention relates generally to spacecraft isolation systems and, more particularly, to launch lock assemblies with reduced preload and spacecraft isolation systems including the same.BACKGROUND[0003]Control moment gyroscope arrays, reaction wheel arrays, and other such devices deployed onboard spacecraft for attitude adjustment purposes generate vibratory forces during operation. Spacecraft isolation systems are commonly employed to minimize the transmission of vibratory forces emitted from such attitude adjustment devices, through the spacecraft body, to any vibration-sensitive components (e.g., optical payloads) carried by the spacecraft. Spacecraft isolation systems commonly include a number of individual vibration isolators (typically three to eig...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): B64G1/00B64G1/64B64G1/22B64G1/28
CPCB64G1/641B64G1/283B64G1/285B64G1/286B64G2001/228B64G1/228
Inventor BARBER, TIM DANIELYOUNG, KENHINDLE, TIMOTHY
Owner HONEYWELL INT INC
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